Effects of Co and Nb on the Crack of Additive Manufacturing Nickel-Based Superalloys

doi:10.1007/s40195-024-01726-9

Abstract

Abstract:

Increasing the print quality is the critical requirement for the additive manufactured complex part of aero-engines of nickel-based superalloys. A study of the effects of Co and Nb on the crack is performed focusing on the selective laser melting (SLM) nickel-based superalloy. In this paper, the solvus temperature of γ', crack characteristics, microstructure, thermal expansion, and mechanical properties of SLM nickel-based superalloy are investigated by varying the content of Co and Nb. The alloy with 15Co/0Nb shows the highest comprehensive quality. Nb increases the crack risk and thermal deformation, and then Co accelerates the stress release. Therefore, Co is an extremely important alloying element for improving the quality of SLM nickel-based superalloy. Finally, the crack growth kinetics and the strain difference are discussed to reveal the SLM crack regular that is affected by time or temperature. The analysis work on the effect of alloying elements can obtain an effective foundational theory to guide the composition optimization of SLM nickel-based superalloys.

Key words: Nickel-based superalloys, Selective laser melting, Element effect, Crack

Kejie Tan, Jinli Xie, Hailong Qin, Bin Xu, Guichen Hou, Jinguo Li, Zhongnan Bi, Ji Zhang. Effects of Co and Nb on the Crack of Additive Manufacturing Nickel-Based Superalloys[J]. Acta Metallurgica Sinica (English Letters), 2024, 37(9): 1601-1610.

Figures/Tables 11

Table 1 Compositions of the TSGH samples (wt%)

Alloys	Co	Nb	Ti	Al	Cr	W	Mo	C	B	Zr	Ni
TSGH-1	0	1	4.5	2.3	14.0	1.2	2.8	0.02	0.02	0.03	Bal.
TSGH-2	15.0	0	5.5	2.3	14.0	1.2	2.8	0.02	0.02	0.03	Bal.
TSGH-3	15.0	1	4.5	2.3	14.0	1.2	2.8	0.02	0.02	0.03	Bal.
TSGH-4	25.0	0	5.5	2.3	14.0	1.2	2.8	0.02	0.02	0.03	Bal.

Fig. 1 Phase transformation temperature measured by DSC, including the solvus temperatures of γ' and solidus temperatures

Fig. 2 X-Y plane optical micrographs after holding temperature at 850 °C with holding time of 10 min for a-d and holding time of 240 min for e-h

Fig. 3 Statistical crack proportions on holding 0, 10, 60, and 240 min, respectively

Fig. 4 EBSD-IPF maps to observe the cracks location in X-Y plane of the alloys holding for 10 min

Fig. 5 X-Z plane microstructure of the TSGH alloys held for 10 min by ECCI

Fig. 6 Strain of thermal expansion in the heating and cooling process

Table 2 Strain difference of heating and cooling

Alloys	500 °C	600 °C	700 °C	800 °C	900 °C
TSGH-1	1.43×10⁻³	1.35×10⁻³	1.31×10⁻³	0.99×10⁻³	0.94×10⁻³
TSGH-2	1.03×10⁻³	0.96×10⁻³	0.88×10⁻³	0.84×10⁻³	0.82×10⁻³
TSGH-3	1.39×10⁻³	1.28×10⁻³	1.17×10⁻³	0.94×10⁻³	0.84×10⁻³
TSGH-4	0.42×10⁻³	0.35×10⁻³	0.22×10⁻³	0.18×10⁻³	0.15×10⁻³

Fig. 7 Tensile curve of the four TSGH as-built alloys at 650 °C

Fig. 8 Avrami crack growth kinetics relationship of the four TSGH alloys

Fig. 9 Strain difference depending on temperature of the four TSGH alloys

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